Turbines



0. THEIMER March 20, 1962 TURBINES 7 Sheets-Sheet 1 Filed April 29, 1958 INV NTOR. @Aw

7 SheetsSheet 2 INVENTOR. firm TURBINES O. THEIMER March 20, 1962 Filed April 29, 1958 0. THEIMER March 20, 1962 TURBINES 7 Sheets-Sheet 3 Filed April 29, 1958 INVENTOR.

March 20, 1962 o. THEIMER 3,026,086

TURBINES Filed April 29, 1958 7 Sheets-Sheet 4 FIG 4 0. THEIMER March 20, 1962 TURBINES Filed April 29, 1958 7 Sheets-Sheet 5 0. THEIMER March 20, 1962 TURBINES '7 Sheets-Sheet 6 Filed April 29, 1958 March 20, 1962 o. THEIMER 3,026,086

TURBINES Filed April 29, 1958 7 Sheets-Sheet 7 IN VEN TOR.

United States Patent 01 3,026,086 TURBINES Oscar Theimer, 35 Fort Washington Ave., New York, N.Y. Filed Apr. 29, 1958, Ser. No. 731,760 9 Claims. (Cl. 253-3915) This invention refers to improvements relating to turbines, in particular to the turbine rotor as disclosed in my US. Patent No. 2,524,549 dated October 3, 1950, and to further improvements disclosed in my patent application Serial No. 450,180 filed August 16, 1954, now abandoned.

It is a primary object of this invention to provide means considerably increasing the economy and efficiency of the turbine rotor and simplifying and strengthening the construction thereof while simultaneously reducing the weight.

It is another object of the invention to provide means facilitating easy assembly and installation of the turbine rotor.

There and other objects and advantages of this invention will become more apparent as the following description of the invention progresses, which is illustrated in the attached drawings, in which:

FIG. 1 is a horizontal section of the turbine seen in FIG. 2 in which the injection nozzles are located in one group on one side along the outer rotor periphery; the inner guide body is separated by division walls.

FIG. 2 is a vertical sectional view of the turbine seen in FIG. 1 embodying my invention.

FIG. 3 is a horizontal section of a modified form of the turbine in which the injection nozzles are located only on one side along the outer rotor periphery, the inner guide body is not separated by division walls.

FIGS. 4, and 6 are fragmentary sectional views of details of the rotor, the sections being taken along lines 44, lines 5-5 and lines 66 of FIG. 7.

FIG. 4a is a fragmentary sectional View of details of the rotor in which the rotor blades are shown in the form of tubes of polygonal shape.

FIG. 7 is a perspective view of the rotor.

FIG. 8 is a horizontal view of another modification embodying the invention with injection nozzles located all around the outer rotor periphery.

FIG. 9 is a vertical sectional view taken along lines 9-9 of FIG. 8.

Referring more particularly to the drawings, FIGS. 1 to 3 illustrate preferred embodiments of the invention, in which the flow of a power medium is guided from nozzles 40 located in turbine stationary casing 3 into a rotating inner guide body 4 of rotor 1 as hereinafter in detail described.

The turbine rotor 1 is divided into three sections, namely a first and second outer rotor cooling section indicated by 0.8., and a rotor middle section indicated by M.S. (FIGS. 5, 6 and 7).

Said rotor sections are constituted by respective innerand outer rotor discs 12, 12a and 13a, 13, which are secured to rotor shaft 2 in predetermined distances and comprises respective rotor cooling canals 19 and rotor power canals 17 disposed between said respective inner and outer rotor discs (FIGS. 2, 9).

Within both outer rotor cooling sections 0.8. are located the aforesaid rotor cooling canals 19 and within 3,926,635 Patented Mar. 20, 1962 ice the rotor middle section M.S. are located in alternate sequence said rotor cooling canals 19 sometimes hereinafter called rotor cooling medium directing means, and rotor power canals 17, sometimes called hereinafter rotor power medium directing means.

Cooling medium and power medium are separately circulating through said respective rotor canals, which are disposed between said outer and inner rotor discs, constituting a rotating housing or enclosure for flow of said cooling medium and power medium respectively, said rotating housing or enclosure is revolving within a stationary turbine housing or casing.

Between the inner rotor periphery 1b and shaft 2 are provided from one end to the other end in axial direction of the rotor 1 (FIG. 2) three chambers 18, 18a, 18b in superposed position, of which chambers 18, 18b located in said two outer cooling sections 0.8., are provided for supply of air or other suitable cooling medium for the rotor 1.

Chamber 18a located in said middle rotor section M.S. is defined by said rotating inner guide body, which is divided by partition walls 52b, 53b in guide pockets 52, 53, constituting a first and second guide body section (FIGS. 1, 2, 3).

Said rotating inner guide body 4 in the turbine rotor 1 (FIG. 2) is constituted by the center portions of inner rotor discs 12a and 13:: within the middle rotor section.

Rotor blades C defining fiuid conveying means, form respective parts of rotor canals 17 and 19.

Both types of rotor canals extend radially from the inner rotor periphery 1b to near the outer rotor periphery in (FIGS. 2, 3, 4, 5, 6, 7), said inner periphery 1b being spaced radially from the rotor shaft 2 (FIGS. 1, 2 and 3).

Said rotor cooling canals 19 within the rotor middle section M.S. are sealed oif at their ends at the outer and inner rotor peripheries against entrance of power medium, by plates or other means 21a, 21b (FIGS. 1, 3, 4, 5, 7, 8) and have therebetween openings respectively apertures 19a, 1% (FIGS. 1, 4, 5, 8) or at least one large opening respectively aperture in inner rotor discs 12a, 13a (left side of FIG. 4) to provide air circulation between the rotor cooling canals 19 sealed against entrance of power medium and located within said rotor middle section and the cooling canals 19 located within both outer rotor cooling sections, which cooling canals are open at both ends to allow said circulation of cooling medium as hereinafter in detail described (FIGS. 2, 5, 6 and 9).

Said rotating inner guide body 4 within the rotor middle section according to modification of FIGS. 1, 2, 3 is intended for the radial passage of the power medium on its way via said nozzles 40 through the respective rotating power canals 17 located within the rotor middle section M.S. and through said inner rotating guide body '4 into the respective adjacent rotating power canals 17, to be thereafter ejected from the outer rotor periphery into the open air (FIGS. 1, 2, 3).

In the modifications of FIGS. 1, 2, 3, the center portions of inner rotor discs 12a, 13a are simultaneously constituents of the rotating inner guide body 4; further, central sleeve 34b is protecting said shaft 2 against direct heat contact and the power medium rotor canals against entry of cooling medium passing through cut outs 14 of the outer rotor discs 12, 13 and through orifices 14b of the inner rotor discs 12a, 13a into said sleeve 34b (FIG. 2). Said central sleeve 34b is fixedly connected with the center portions of said inner rotor discs 12a, 13a and spaced from said shaft 2 and revolving therewith, which shaft 2 extends through rotor discs 12, 12a, 13a, 13 (FIG. 2); all said discs being directly connected and revolving with said shaft 2.

Inner rotor discs 12a, 13a are close to shaft 2 provided with orifices 14b (FIG. 2) to make possible air circulation from the chambers 18, 18b within the two outer rotor sections 0.8. adjoining in axial direction both sides of said rotor discs 12a, 13a (FIG. 2) through said sleeve 34b, which surrounds shaft 2 in near distance within the middle rotor section, in order to cool very efficiently the portion of said shaft 2, extending through said rotating inner guide body 4.

The cooling medium enters the rotor in axial direction by automatic suction because of existing atmospheric pressure through cut outs 37 in the turbine stationary casing plates 6 and 7 and cut outs 14 in the rotor center of outer rotor discs 12, 13 into said rotor air chambers 18, 18b located within both said outer rotor cooling sections 0.5., thence being directed radially into said cooling canals 19, radially disposed between rotor discs 12, 12a on one side and between rotor discs 13a, 13 on the other side, which cooling canals form constituents of both outer rotor cooling sections. From these cooling canals 19 within both outer rotor cooling sections 0.8. the cooling medium passes through apertures 19a (FIGS. 2, 5) located near the inner rotor periphery 1b (FIG. 1) in each one of rotor discs 12a, 13a (FIG. 5) into the rotor cooling canals 19 located in alternate sequence with the rotor power canals 17 within the rotor middle section to be then after passing radially through said rotor inner cooling canals 19 expelled and returned through apertures 19b (FIGS. 2, 5) near the outer rotor periphery in each one of rotor discs 12a, 13a (FIG. 5) into the predetermined respective side 'by side therewith adjoining outer cooling canals 19 located within both outer rotor cooling sections 0.5. (FIG. 5) to be then expelled at the outer rotor periphery on account of existing centrifugal force during enormous high rotor speed with great power into the atmosphere (FIGS. 2, 5, 9) causing additional rotor power by repulsion, similar to jet reaction.

The extreme violent circulation of the cooling medium through said cooling canals 19 within the rotor middle section very effectively cools large portions of the surfaces of the power canals 17 within said rotor middle section, while the circulation of the cooling medium through the cooling canals 19 within both outer rotor cooling sections, which latter cooling canals 19 located 1 side by side to said power canals 17 within said rotor middle section cool very effectively the remaining portions of said power canals 17 located within said rotor middle section.

If instead of rotor blades C within the rotor middle section M.S. rotor tubes are employed and inserted between rotor discs 12a, 130, not only said rotor discs themselves but also the inserted rotor tubes which are designated for the cooling tubes 19 are each to be provided at the corresponding positions with at least one substantially large aperture for circulation of a cooling medium, between the two outer rotor cooling sections 0.8. and the rotor middle section M.S. (FIG. 5).

Further referring particularly to FIGS. 4, 5, 6 and 7, details seen therein are as follows:

The rotor air cooling canals 19 and the power canals 17 in FIG. 4 are located in alternate sequence within the rotor middle section M.S. One of said shown rotor cooling canals 19 has two apertures 19a, 195, whereas the other shown rotor cooling canal 19 has only one large aperture extending from one canal end to the other canal end.

Two of the rotor air cooling canals 19 in FIG. 5 are located in the two outer rotor cooling sections 0.8., and

the third air cooling canals 19 are located in the rotor middle section M.S.

According to FIG. 6 the rotor air cooling canals 19 are located in the two outer rotor cooling sections 0.8., and the rotor power canals 17 is as shown located in the rotor middle section.

FIG. 7 which is a perspective View of the rotor with partially cut outs of rotor disc 12, shows two outer rotor cooling sections 0.8. indicated at the right hand side of the respective canal rows including only rotor air cooling canals 19, further showing one rotor middle section M.S., also indicated at the right hand side of the respective canal row including in alternate sequence located rotor power canals 17 and rotor air cooling canals 19; said rotor air cooling canals 19 located in said middle rotor section are at both ends covered by plates 21a, 21b or other means, indicated by dotted lines (FIGS. 5, 7) and by hatched lines (FIGS. 1, 3, 4, 8) to prevent entrance of hot power medium.

Referring to rotating inner guide body 4, the performance of the power medium circulating radially therethrough takes place in such a manner, that the power medium ejected from the rotating power canals 17 into guide pocket 52 of the first guide body section (FIGS. 1, 2, 3) exert thereby in addition to its main driving impulse and pressure (action) on the rotor during passage through the power canals 17 useful work upon the rotor by repulsion during its ejection. The power medium is guided substantially straight and along the shortest path within said guide pocket 52 into the adjacent by passing rotating power canals 17 repeating the same performance, from where the power medium is directly expelled into the open air at the outer rotor periphery, exerting thereby again useful work upon the rotor.

This useful work exerted by repulsion is similar to jet reaction. The same performance of the power medium takes place in the inner guide pocket 53 of the second guide pocket section, as is understood. The power medium when onrushing against the peculiarly curved rotor blades C, which are constituting portions of the power canals 17, also of the cooling canals, work upon the rotor by impact (action) and during its passage therethrough by impulse and pressure in consequence of its expansion and is also supported by useful friction of the power medium in direction of the rotor movement, further by repulsion (reaction) because with great force expelled at the outer rotor periphery by centrifugal force.

Rotor discs 12, 12a, 13a, 13 are enclosing rotor blades C, forming jointly cooling medium rotor directing means and power medium rotor directing means which constitute simultaneously a revolving housing or enclosure. Within the respective rotor directing means are cooling medium and power medium separately circulating in enclosed condition.

The rotor forms a revolving housing or body within the stationary outer guide body respectively casing 3.

In the present instance the rotor canals, tubes, or like are substantially oblong as the drawings show, and the profile of the power canals or tubes 17 have throughout their length the same square measurement in order to ensure equal flow of power medium throughout the entire length of the power canals 17.

lerfonnance and proceedings of the power medium, as well as the circulation of the cooling medium within these improved and simplified turbine rotor modifications pursuant to FIGS. 1, 2 and 3 takes place in the same way and manner, while in modification pursuant to FIGS. 8, 9 they are carried out according to hereinafter specificated description.

Very small and insignificant power output is lost in spite of air suction and air expulsion of huge masses of cooling air circulating during rapid revolution of the turbine rotor, but is in four ways almost fully compensated for, first by impact of the vigorous onrushing airflow entering through openings 37 provided in the housing plates 6, 7 and by way of rotor center cut outs 14 in outer rotor discs 12, 13 (FIGS. 2, 9) against the peculiar curved rotor blades C (FIGS. 1, 3, 8), secondly by impulse and pressure during the enormously rapid passage of the cooling air through the rotor air cooling canals 19, thirdly by repulsion (reaction) of the airflow when expelled with great force from the rotor air cooling canals 19, at the outer rotor periphery 1a (H68. 2, 5, 6, 7 and 9). Fourth: In consequence of the peculiar arranged rotor construction, there is substantially no harmful friction between the respective circulating medium and a stationary turbine casing, because the respective circulating medium enclosed in the respective rotor canals does not come in contact therewith, contrary there is only useful friction in direction of rotation between the circulating medium and the rotor canal walls within the rotating housing respectively rotor discs thereby increasing the driving force respectively the turbine power output. Said rotor canals are im wdded between said rotor discs 12, 12a, 13a, 13, for which reason the cooling medium and power medium are rotating in enclosed condition. The air cooling flow acts during said performance in about the same way and manner as the gasflow when circulating through the turbine rotor.

The onrushing airflow against the peculiarly curved rotor blades respectively rotor canals is working in a similar manner as the wind when striking against the blades of a wind mill.

To increase the efiiciency of cooling the hot walls of the rotor power canals 17, if desired, freezers F, air conditioners or other cooling means may be arranged at opposite sides, between the turbine housing plates 6 and 7 and the rotor 1, as for instance shown in FIGS. 2 and 9, cooling additionally through cut outs 14a between the outer and inner rotor periphery of outer rotor discs 12 and 13, the incoming and bypassing airflow on its way to the rotor air cooling canals 19 and along outside the hot walls of the power canals 17.

The rotor power canals, tubes 17, and the rotor cooling canals, tubes 19, are curved, forming preferably a part of an absolute or an approximate logarithmic spiral. Said rotor canals or tubes 17 and 19 are curved in the direction of the rotor movement, and curved at opposed ends; these curvatures at opposed ends are situated with respect to the inner and outer rotor peripheries in an angle directly opposite to the direction of the rotor movement.

Due to the fact that the power and cooling medium are simultaneously moving in enclosed condition while passing through the respective revolving canal means 17 and 19 within the rotor itself, contact and detrimental friction of the power and cooling medium with the walls of the stationary turbine casing 3 during their passage through the turbine is effectively and almost entirely eliminated.

For the aforesaid and other purposes the turbine according to the invention disclosed in my Patent No. 2,524,549 issued October 3, 1950, has been improved and greatly simplified by eliminating either all or a number of the outer guide pockets, the inner guide pockets with numerous guide members, the outer rotor rim member, the inner stationary guide body being replaced by an inner rotating guide body, the stationary sleeve being replaced by a rotating sleeve and further eliminated are sleeve support, some ball bearings, the inner gas trap sealing device constituted by rotor disc extension and annular grooves within the inner stationary guide body.

FIGS. 8 and 9 illustrate a modification pursuant to the invention for use in airplanes.

Rotor 200 has a chamber 18 to allow passage therethrough of atmospheric air pressed into its nose N during forward movement of the airplane, as well as to allow exhaust gas to enter chamber 18 which gas is injected thereinto from the power medium canals 17 located in alternate sequence with the cooling medium canals 19 within the rotor middle sections M.S. Said latter cooling medium canals 19 are sealed at both ends to prevent the entrance of said power medium. The atmospheric air pressed into chamber 18, as well as said exhaust gas injected thereinto from rotor power canals 17 within the rotor middle section are jointly expelled into the open air through the tail end T of said chamber 18.

Rotor chamber 18 in the middle rotor section M.S. is not sealed off according to above description in axial direction by means of the center portions of rotor discs 12a, 13a, which form in the modification of FIGS. 2 and 3 portions of the rotating inner guide body 4, intended for radial passage of power medium therethrough. The center portions of rotor discs 12a, 13a and of the rotor discs 12, 13, as well as portions in the center of the casing plates 6, 7 are according to the modification of FIGS. 8, 9 cut out to provide openings 37 and cut outs 14, 14a to allow abundant air and gas inlet and outlet according to arrows A and G; further this rotor chamber 18 is sealed off within both outer rotor cooling sections 0.8. in some distance from and about shaft 2 by division tubes D, thereby separating said rotor chamber 18 along shaft 2 in an outer ring shaped rotor chamber 18a and an inner tubular shaped rotor chamber 18.

Between the inner end of the rotor cooling canals 19 which are reduced in length and located within the first and second outer rotor cooling sections 0.8. and said division tubes D, are provided in each outer rotor cooling section said ring shaped outer rotor chambers 1811, allowing entrance of atmospheric air by suction in axial direction through cut outs 37 provided in casing plates 6, 7 and cut cuts 14 in outer rotor discs 12, 13 and then flowing in radial direction into the inner ends of and through said rotor cooling canals 19 within said first and second outer rotor cooling sections; said rotor cooling canals reduced in length terminate some distance from and about said division tubes D (FIG, 9) cooling the adjacent hot walls of the rotor power medium canals 17 within the middle rotor section MS, which power medium canals 17 are entirely surrounded by said rotor cooling canals 19 located on the one side in alternate sequence with the power medium rotor canals 17 within said middie rotor section MS. and on the other side located in both outer rotor cooling sections MS.

The construction of the cooling system and the method of cooling proceedings are identical in the modifications shown in FIGS. 1, 2, 3, 8 and 9.

The portion of the rotor chamber 13 located within the middle rotor section M5. is not used pursuant to this modification as inner guide body 4, but only as before mentioned as passage means in axial direction for atmospheric air pressed or rammed into said nose N of chamber 18 and the exhaust gas injected thereinto from the power medium canals 17 within the middle rotor section.

In the modification of FIGS. 8, 9 the injection nozzles 49 are disposed all around the entire rotor periphery. The rotor power medium directing means 17 and said cooling medium directing means 19 are located in alternate sequence within said middle rotor section, and extend from the outer rotor periphery in the direction of the inner rotor periphery (FIG. 9) said power medium directing means protrude beyond said rotor cooling canals .19 located within both outer rotor cooling sections, as well as beyond said division tubes D spaced in some distance from shaft 2. The exhaust gas and air is expelled from the turbine into the atmosphere through the tail end T of said division tube D, and exert during expulsion on account of repulsion, acting in the same manner as the gas and air expulsion into the atmosphere from jet airplanes, tremendous useful work upon the airplane.

If preferred the two outer gas traps sealing devices 24 within the outer stationary guide body forming turbine casing (H68. 2, 9) may also be eliminated, only nozzles 4-9 alone being located within said turbine casing 3 extend partially between extensions 22 or rotor discs 12a and 13a (FIG. 10).

On account of said eliminations, undesirable friction 7 is greatly reduced and the turbine construction is greatly simplified and considerably reduced in Weight.

Turbine modification of FIGS. 8, 9 is as before pointed out designed for use in airplanes; the turbine airplane is simultaneously put in motion by the turbine propeller (not shown) and by jet propulsion, caused by repulsion of the exhaust gas together with the air pressed or rammed into the airplane nose N and with utmost force expelled through the tail end T of the division tube D into the atmosphere.

The turbine casing, as well as the rotor and its various parts may be constructed as a unit from a casting, or in sections made of castings to facilitate assembling of the turbine.

Means may be provided to overcome various difficulties, arising from different peculiarities of the rotor material used, as are: strain, stress, pull, tension, creep, thermal expansion in consequence of the high temperatures of the power medium.

Means to overcome said mentioned difficulties, are to assemble interchangeably the separate substantially rotor parts, such as rotor discs, rotor blades, strips or tubes and other parts, by such assembling means, as are for instance2threaded bolts 1G9 passing through and beyond the respective rotor discs at such places which are not in direct contact with the hot gases. Between said rotor discs are imbedded said rotor blades, strips or tubes C,

' etc. Said rotor discs are secured to said threaded bolts 100 by nuts 1G1 pressing against very strong special springs 102 or compressed air cushions or other elastic, self adjusting shock and pressure resisting means, permitting expansion and contraction of the rotor material, in such a manner, that all assembled rotor parts form a compact structure, safely withstanding the high centrifugal force because of the enormous rotor speed, and all other mentioned forces (FIG. 7).

This new method of assembling, mounting and dismounting of rotors exchange of rotor parts, repairs, cleaning as well as reassembling of rotors is most simple and accomplished in much less time as rotors can be assembled according to usual assembling methods, as by welding, soldering, etc.

If not detrimental to the compactness, tear-pull and strain resistance, required of the rotor material on account of excessive heat and enormous centrifugal force, for the purpose of further improvement of the cooling capacity, porous rotor material or rotor material with tiny slots may be used, to enable besides convection also transpiration or film cooling.

It is well understood in accordance with the above description and drawings herein submitted, that deviations and changes may be made from the embodiments herein set forth, without departing from the spirit and scope of this invention.

Having thus described the invention, what is claimed as new and desired-to be secured by Letters Patent, is:

l. A turbine structure comprising a stationary turbine casing provided with intake openings, a shaft, a rotor connected with said shaft for rotation therewith and including an inner and an outer periphery, said rotor being defined by outer discs and opposite inner rotor discs spaced from said outer rotor discs, a rotable guide body formed by parts of said inner rotor discs, a plurality of rotor blades, said inner and outer rotor discs being concentric with each other and spacedly mounted upon said shaft, a number of said plurality of rotor blades extending axially from each one of the outer rotor discs to each one of the inner rotor discs and also extending inward in circumferentially spaced relation from the outer perimeter of said inner and outer rotor discs and radially in the direction of said rotor shaft and terminating at the inner perimeter, the remaining rotor blades located between said inner rotor discs extending axially from both inner rotor discs and extending also inward in circumferentially spaced relation from the outer perimeter of said both inner rotor discs and radially in the direction of said rotor shaft and terminating at the inner rotor periphery between said inner rotor discs, the space between said inner rotor periphery and said shaft defining said rotatable inner guide body, said axial and inward extending rotor blades and each outer and each inner opposite spaced rotor disc forming together outer cooling medium rotor canals open at opposite ends thereof, said remaining rotor blades and both said opposite spaced inner rotor discs forming together power medium rotor canals, and cooling medium rotor canals, respectively, the cooling medium rotor canals being sealed at opposite ends, said inner rotor discs constituting alternately portions of said inner and outer cooling medium rotor canals and said power medium rotor canals, the portions of said inner rotor discs being portions of said inner and outer rotor cooling medium canals and having near the inner rotor perimeter a passageway to permit flow of a cooling medium from the adjoining outer cooling medium rotor canals to the inner cooling medium rotor canals and being radially guided from the inner to the outer rotor periphery along the inner cooling medium rotor canals toward a passageway provided in said inner rotor discs near its outer periphery to escape therethrough into the adjoining outer cooling medium rotor canals to be expelled therefrom at the outer rotor periphery into the atmosphere, said outer and inner cooling medium rotor canals jointly surrounding said power medium rotor canals, each of said outer rotor discs being provided with central cut outs for the passage of incoming cooling air from the atmosphere, said inner rotor discs being provided in the proximity of said rotor shaft with orifices which are in communication via said cut outs in said outer rotor discs with said intake openings of said staouter rotor discs for additional cooling medium supply,

thereby to intensify the cooling efiect of said cooling medium.

3. A structure as set forth in claim 1, comprising a centrally located sleeve fixedly connected with center portions of said two inner rotor discs, said sleeve forming a hollow enclosure of predetermined length and diameter and surrounding said shaft for rotation therewith, said orifices communicating with said enclosure for protection of said shaft against direct heat contact, said sleeve preventing cooling medium from passing by way of said orifices into the power medium rotor canals located within said two inner rotor discs.

4. A structure set forth in claim 3, comprising two outer rotor cooling sections and a rotor middle section, both said outer rotor sections and said middle section enclosing therebetween said cooling canals, said outer rotor cooling sections facilitating the supply of cooling medium to said rotor cooling canals and to said shaft, said middle rotor section including said centrally located sleeve.

5. A structure according to claim 4, including said first and second outer rotor cooling sections comprising a plurality of rotor cooling medium canals radially extending from the outer to the inner rotor periphery, an open tubular chamber axially extending throughout said rotor w and defined by tubular partition walls throughout said first as well as said second outer rotor cooling sections, an outer open ring shaped rotor chamber surrounding said tubular chamber.

6. A structure as set forth in claim 1, including nozzle 'rneans located within said stationary casing, said middle 9 10 medium rotor canals through said rotating inner guide 9. A turbine structure according to claim 1, said rotor body into power medium rotor canals remote from said blades being of tubular formation. nozzle means.

7. A turbine structure according to claim 1, including References Cited ill the file of this Patent a revolving housing for power medium and cooling medi- 5 UNITED STATES :PATENTS um, said revolving housing being rotatable within said stationary turbine casing. ,723,515 Koch Aug. 6, 1929 8. A turbine structure according to claim 1, said rotor ,837,717 Koch Nov. 15, 1932 canals and said rotor discs forming together said revolv- 2, 2 9 Theimer Oct. 3, 1950 ing housing within said stationary turbine casing. 10 ,783,964 Theimer Mar. 5, 1957 

